Connection structure of exhaust chamber, support structure of turbine, and gas turbine

ABSTRACT

In a gas turbine, an exhaust casing and an exhaust chamber are connected by an exhaust chamber support that can absorb thermal expansion, and the exhaust chamber and an exhaust duct are connected by an exhaust duct support that can absorb thermal expansion. An insulator is mounted on an outer peripheral surface of the exhaust chamber, and the exhaust chamber support and the exhaust duct support are disposed outside the insulator in the form of a plurality of strips. Because the thermal stress at a connection portion of the exhaust chamber is reduced, the durability is enhanced.

RELATED APPLICATIONS

The present application is a divisional of U.S. patent application Ser.No. 12/919,530 filed on Aug. 26, 2010, which is based on InternationalApplication Number PCT/JP2009/051280, filed on Jan. 27, 2009, and claimspriority from Japanese Application Numbers 2008-046699, filed on Feb.27, 2008 and 2008-088744, filed on Mar. 28, 2008. The contents of all ofthe above-listed applications are incorporated by reference herein intheir entirety.

TECHNICAL FIELD

The present invention, for example, in a gas turbine that obtainsrotational power by supplying fuel to high-temperature and high-pressurecompressed air, burning the compressed air and fuel, and supplying theproduced combustion gas to a turbine, relates to a connection structureof an exhaust chamber disposed at a rear of the turbine, and a gasturbine to which the connection structure of the exhaust chamber isapplied.

The present invention, for example, in a gas turbine that obtainsrotational power by supplying fuel to high-temperature and high-pressurecompressed air, burning the compressed air and fuel, and supplying theproduced combustion gas to a turbine, also relates to a supportstructure of a turbine for mounting the turbine on the floor, and a gasturbine to which the support structure of the turbine is applied.

BACKGROUND ART

A gas turbine includes a compressor, a combustor, and a turbine. Airtaken in from an air inlet port is turned into high-temperature andhigh-pressure compressed air, by being compressed by the compressor. Inthe combustor, fuel is supplied to the compressed air to be combusted.The high-temperature and high-pressure combustion gas drives theturbine, and drives a generator connected to the turbine. In this case,the turbine includes a casing in which a plurality of nozzles and rotorblades are alternately arranged. An output shaft connected to thegenerator is rotatably driven because the rotor blades are driven by thecombustion gas. The combustion gas that drove the turbine is convertedinto static pressure by a diffuser in an exhaust casing and thenreleased to the atmosphere.

In recent years, higher power and higher efficiency are demanded for thegas turbines formed in this manner, and the temperature of combustiongas guided to the nozzles and rotor blades has been increased.Accordingly, in general, a cooling passage is formed inside the nozzlesand rotor blades, and the nozzles and rotor blades are cooled by runningcoolant medium such as air and steam through the cooling passage.Consequently, while maintaining the heat resistance, the temperature ofcombustion gas is increased, thereby increasing the power and efficiencyof the gas turbine.

For example, in the turbine, an exhaust chamber is connected to thedownstream of the exhaust casing in which the nozzles and rotor bladesare stored, and an exhaust duct is connected to the downstream of theexhaust chamber. The exhaust casing and the exhaust chamber areconnected by a thermal expansion absorbing member in the form of acylindrical sheet, and the exhaust chamber and the exhaust duct areconnected by an expansion joint having an insulator. Accordingly, thethermal stresses between the exhaust casing, the exhaust chamber, andthe exhaust duct are absorbed, during heavy load operation and a powerincrease of the gas turbine.

For example, Patent Documents 1, 2, and 3 below disclose this connectionstructure of a turbine.

A gas turbine includes a compressor, a combustor, and a turbine. Airtaken in from an air inlet port is turned into high-temperature andhigh-pressure compressed air, by being compressed by the compressor. Inthe combustor, fuel is supplied to the compressed air to be combusted.The high-temperature and high-pressure combustion gas drives theturbine, and drives a generator connected to the turbine. In this case,the turbine includes a casing in which a plurality of nozzles and rotorblades are alternately arranged. An output shaft connected to thegenerator is rotatably driven because the rotor blades are driven by thecombustion gas. The combustion gas that drove the turbine is convertedinto static pressure by a diffuser in an exhaust casing and thenreleased to the atmosphere.

In the gas turbine formed in this manner, the exhaust casing in whichthe nozzles and rotor blades are stored, the exhaust chamber, and theexhaust duct formed in cylindrical shapes are connected, and mounted onthe floor in a building by a plurality of legs. The exhaust casing, theexhaust chamber, and the exhaust duct have a double cylindrical shape,because the outer casing and the inner casing are connected by a strut,and a space between the outer casing and the inner casing is a passagefor exhaust gas. The legs are connected to both sides of the outercasing, and the exhaust casing, the exhaust chamber, and the exhaustduct are mounted on the floor by the legs.

For example, Patent Document 4 discloses this support structure of aturbine.

-   [Patent Document 1] Japanese Patent Application Laid-open No.    2006-307733-   [Patent Document 2] Japanese Patent Application Laid-open No.    2004-308502-   [Patent Document 3] Japanese Utility Model Application Laid-open No.    H01-085429-   [Patent Document 4] Japanese Patent Application Laid-open No.    H07-293277

DISCLOSURE OF INVENTION Problem to be Solved by the Invention

In the conventional gas turbine described above, the thermal stressbetween the members are absorbed by connecting the exhaust casing andthe exhaust chamber by a thermal expansion absorbing member in a sheetshape or by connecting the exhaust chamber and the exhaust duct by anexpansion joint. However, the temperature of the combustion gas has beenfurther increased, because higher power and higher efficiency aredemanded for the gas turbine, thereby making it difficult to select thethermal expansion absorbing member and to ensure the heat resistance ofthe expansion joint. Accordingly, the thermal expansion absorbing memberand the expansion joint may be cooled. However, this leads to theincreased temperature difference between the thermal expansion absorbingmember and the expansion joint, and the exhaust casing, the exhaustchamber, and the exhaust duct, thereby increasing the thermal stress andadversely affecting the durability.

In the conventional support structure of the turbine described above,the legs are connected to both sides of the outer casing of the exhaustcasing, the exhaust chamber, and the exhaust duct. The exhaust casing,the exhaust chamber, and the exhaust duct are mounted on the floor bythe legs. Because the exhaust casing, the exhaust chamber, and theexhaust duct are heavy goods, the bending stress is applied to fixingportions of the legs at the outer casing, thereby causing deformation orthe like to them. Accordingly, a rib is provided at the outer peripheralsurface of the outer casing in the circumferential direction, and thelegs are connected interposing the rib therebetween.

However, during the turbine is in operation, the thermal expansionoccurs because the temperature of the outer casing of the exhaustcasing, the exhaust chamber, and the exhaust duct is increased by theexhaust gas. If this occurs, the thermal expansion amounts at the outercasing, between a portion where the strength is increased by the rib andthe other portion differ, thereby generating thermal stress.Accordingly, the deformation, the breakage, and the like may occur.

The present invention has been made to solve the problems above, and anobject of the present invention is to provide a connection structure ofan exhaust chamber and a gas turbine for enhancing durability, byreducing the thermal stress at a connection portion of the exhaustchamber.

The present invention has been made in view to solve the above problems,and an object of the present invention is to provide a support structureof a turbine and a gas turbine for enhancing durability, by reducing thebending stress and the thermal stress applied to a turbine main body.

Means for Solving Problem

According to an aspect of the present invention, a connection structureof an exhaust chamber in which an exhaust chamber formed in acylindrical shape and a connection member formed in a cylindrical shapedisposed upstream or downstream of the exhaust chamber in a flowingdirection of exhaust gas are connected by a support member that iscapable of absorbing thermal expansion, includes: an insulator mountedon an outer peripheral surface of the exhaust chamber. The supportmember is disposed outside the insulator in a form of a plurality ofstrips, and one end thereof is connected to an end of the exhaustchamber and another end is connected to an end of the connection member.

Advantageously, in the connection structure of the exhaust chamber, theconnection member is an exhaust casing disposed upstream of the exhaustchamber in the flowing direction of the exhaust gas, the insulator ismounted on an outer peripheral surface of the exhaust casing, and theexhaust casing is connected to the exhaust chamber by an exhaust chambersupport as the support member.

Advantageously, the connection structure of the exhaust chamber furtherincludes an exhaust diffuser formed in a cylindrical shape disposedinside the exhaust casing. The exhaust casing and the exhaust diffuserare connected by a diffuser support that is capable of absorbing thermalexpansion in a form of a plurality of strips.

Advantageously, the connection structure of the exhaust chamber furtherincludes a gas seal for connecting the exhaust chamber and the exhaustcasing at an inside of the exhaust chamber support.

Advantageously, in the connection structure of the exhaust chamber, theconnection member is an exhaust duct disposed downstream of the exhaustchamber in the flowing direction of the exhaust gas, the insulator ismounted on an inner peripheral surface of the exhaust duct, and theexhaust duct is connected to the exhaust chamber by an exhaust ductsupport as the support member.

Advantageously, the connection structure of the exhaust chamber furtherincludes an outer shell member formed in a ring shape disposed at anouter peripheral side of the exhaust chamber. The exhaust duct isdisposed adjacent to the outer shell member, the exhaust chamber and theouter shell member are connected by the exhaust duct support, and theouter shell member and the exhaust duct are connected by ahigh-temperature expansion joint.

Advantageously, the connection structure of the exhaust chamber furtherincludes a gas seal that connects the exhaust chamber and the exhaustduct at an outside of the exhaust duct support.

According to another aspect of the present invention, a gas turbine thatobtains rotational power by supplying fuel to compressed air compressedby a compressor, burning the fuel in a combustor, and supplying producedcombustion gas to a turbine, the turbine including an exhaust casing andan exhaust chamber connected by an exhaust chamber support that iscapable of absorbing thermal expansion, and the exhaust chamber and anexhaust duct being connected by an exhaust duct support that is capableof absorbing thermal expansion, includes: an insulator provided at anouter peripheral surface of the exhaust chamber. The exhaust chambersupport is disposed outside the insulator in a form of a plurality ofstrips, and one end thereof is connected to an end of the exhaustchamber, and another end is connected to an end of the exhaust casing.

According to still another aspect of the present invention, a gasturbine that obtains rotational power by supplying fuel to compressedair compressed by a compressor, burning the fuel in a combustor, andsupplying produced combustion gas to a turbine, the turbine including anexhaust casing and an exhaust chamber connected by an exhaust chambersupport that is capable of absorbing thermal expansion, and the exhaustchamber and an exhaust duct being connected by an exhaust duct supportthat is capable of absorbing thermal expansion, includes an insulatorprovided at an outer peripheral surface of the exhaust chamber. Theexhaust duct support is disposed outside the insulator in a form of aplurality of strips, and one end thereof is connected to an end of theexhaust chamber, and another end is connected to an end of the exhaustduct.

Advantageously, the gas turbine further includes an outer shell memberformed in a ring shape disposed at an outer peripheral side of theexhaust chamber. The exhaust duct is disposed adjacent to the outershell member, the exhaust chamber and the outer shell member areconnected by the exhaust duct support, and the outer shell member andthe exhaust duct are connected by a high-temperature expansion joint.

According to still another aspect of the present invention, a supportstructure of a turbine in which a turbine main body formed in acylindrical shape and an outer shell member formed in a ring shapedisposed at an outer peripheral side of the turbine main body areconnected by a support member that is capable of absorbing thermalexpansion, the support structure of the turbine comprising a leg formounting the turbine main body connected to the outer shell member.

Advantageously, in the support structure of the turbine, the turbinemain body includes an exhaust chamber through which combustion gasflows, the exhaust chamber and the outer shell member are connected bythe support member, and the outer shell member is connected to anexhaust duct.

Advantageously, the support structure of the turbine further includes ahigh-temperature expansion joint interposed between the outer shellmember and the exhaust duct.

Advantageously, in the support structure of the turbine, the supportmember is in a form of a plurality of strips, and one end thereof isconnected to an end of the exhaust chamber, and another end is connectedto an end of the outer shell member.

Advantageously, the support structure of the turbine further includes agas seal that connects the exhaust chamber and the outer shell member atan outside of the support member.

Advantageously, in the support structure of the turbine, the supportmember is formed in a truncated cone shape, and one end thereof in anaxial direction is connected to an end of the exhaust chamber, andanother end is connected to an end of the outer shell member.

According to still another aspect of the present invention, a gasturbine that obtains rotational power by supplying fuel to compressedair compressed by a compressor, burning the fuel in a combustor, andsupplying produced combustion gas to a turbine, the turbine including anexhaust chamber and an outer shell member formed in a ring shapedisposed at an outer peripheral side of the exhaust chamber connected bya support member that is capable of absorbing thermal expansion. The gasturbine includes: an exhaust duct connected to the outer shell member;and a leg for mounting the exhaust chamber connected to the outer shellmember.

Means for Solving Problem Effect of the Invention

In the connection structure of the exhaust chamber according to thefirst aspect, the exhaust chamber and the connection member disposedupstream or downstream in the flowing direction of the exhaust gas areconnected by the support member that can absorb thermal expansion. Theinsulator is mounted on the outer peripheral surface of the exhaustchamber. The support member is disposed outside the insulator in theform of a plurality of strips, and one end thereof is connected to theend of the exhaust chamber, and the other end is connected to the end ofthe connection member. Because the support members are formed in strips,the thermal expansion that occurs between the exhaust chamber and theconnection member can be absorbed effectively. Because the supportmember is disposed outside the insulator, the support member issufficiently cooled. As a result, the thermal stress at the connectionportion of the exhaust chamber is reduced, thereby enhancing thedurability.

In the connection structure of the exhaust chamber according to thesecond aspect, the connection member is the exhaust casing disposedupstream of the exhaust chamber in the flowing direction of the exhaustgas, the insulator is mounted on the outer peripheral surface of theexhaust casing, and the exhaust casing is connected to the exhaustchamber by the exhaust chamber support as the support member.Accordingly, the thermal expansion that occurs due to the temperaturedifference between the exhaust chamber and the exhaust casing can beeffectively absorbed, thereby enhancing the durability.

In the connection structure of the exhaust chamber according to thethird aspect, the exhaust diffuser formed in a cylindrical shape isdisposed inside the exhaust casing, and the exhaust casing and theexhaust diffuser are connected by the diffuser support that can absorbthermal expansion in the form of a plurality of strips. Accordingly, thethermal expansion that occurs due to the temperature difference betweenthe exhaust casing and the exhaust diffuser can be effectively absorbed,thereby enhancing the durability.

In the connection structure of the exhaust chamber according to thefourth aspect, the gas seal for connecting the exhaust chamber and theexhaust casing is provided inside the exhaust chamber support.Accordingly, it is possible to prevent the exhaust gas from leaking fromthe connection portion between the exhaust chamber and the exhaustcasing.

In the connection structure of the exhaust chamber according to thefifth aspect, the connection member is the exhaust duct disposeddownstream of the exhaust chamber in the flowing direction of theexhaust gas, the insulator is mounted on the inner peripheral surface ofthe exhaust duct, and the exhaust duct is connected to the exhaustchamber by the exhaust duct support as the support member. Accordingly,the thermal expansion that occurs due to the temperature differencebetween the exhaust chamber and the exhaust duct can be effectivelyabsorbed, thereby enhancing the durability.

In the connection structure of the exhaust chamber according to thesixth aspect, the outer shell member formed in a ring shape is disposedat the outer peripheral side of the exhaust chamber, the exhaust duct isdisposed adjacent to the outer shell member, the exhaust chamber and theouter shell member are connected by the exhaust duct support, and theouter shell member and the exhaust duct are connected by thehigh-temperature expansion joint. Accordingly, the high-temperatureexpansion joint can be suitably cooled, thereby enhancing thedurability.

In the connection structure of the exhaust chamber according to theseventh aspect, the gas seal for connecting the exhaust chamber and theexhaust duct is provided outside the exhaust duct support. Accordingly,it is possible to prevent the exhaust gas from leaking from theconnection portion between the exhaust chamber and the exhaust duct.

The gas turbine according to the eighth aspect includes the compressor,the combustor, and the turbine. The exhaust casing of the turbine andthe exhaust chamber are connected by the exhaust chamber support thatcan absorb thermal expansion, and the exhaust chamber and the exhaustduct are connected by the exhaust duct support that can absorb thermalexpansion. The insulator is mounted on the outer peripheral surface ofthe exhaust chamber. The exhaust chamber support is disposed outside theinsulator in the form of a plurality of strips, and one end thereof isconnected to the end of the exhaust chamber and the other end isconnected to the end of the exhaust casing. Accordingly, because theexhaust chamber supports are formed in strips, the thermal expansionthat occurs between the exhaust casing and the exhaust chamber can beeffectively absorbed, and because the exhaust duct support is disposedoutside the insulator, the exhaust duct support is sufficiently cooled.Consequently, the thermal stress at the connection portion of theexhaust chamber is reduced, thereby enhancing the durability. As aresult, the power and efficiency of the turbine can be enhanced.

The gas turbine according to the ninth aspect includes the compressor,the combustor, and the turbine. The exhaust casing of the turbine andthe exhaust chamber are connected by the exhaust chamber support thatcan absorb thermal expansion, the exhaust chamber and the exhaust ductare connected by the exhaust duct support that can absorb thermalexpansion, and the insulator is mounted on the outer peripheral surfaceof the exhaust chamber. The exhaust duct support is disposed outside theinsulator in the form of a plurality of strips, and one end thereof isconnected to the end of the exhaust chamber and the other end isconnected to the end of the exhaust duct. Accordingly, because theexhaust duct supports are formed in strips, the thermal expansion thatoccurs between the exhaust chamber and the exhaust duct can beeffectively absorbed. Because the exhaust duct support is disposedoutside the insulator, this exhaust duct support is sufficiently cooled.Consequently, the thermal stress at the connection portion of theexhaust chamber is reduced, thereby enhancing the durability. As aresult, the power and efficiency of the turbine can be enhanced.

In the gas turbine according to the tenth aspect, the outer shell memberformed in a ring shape is disposed at the outer peripheral side of theexhaust chamber, the exhaust duct is disposed adjacent to the outershell member, the exhaust chamber and the outer shell member areconnected by the exhaust duct support, and the outer shell member andthe exhaust duct are connected by the high-temperature expansion joint.Accordingly, the high-temperature expansion joint can be suitablycooled, thereby enhancing the durability.

In the support structure of the turbine according to the eleventhaspect, the turbine main body formed in a cylindrical shape and theouter shell member formed in a ring shape disposed at the outerperipheral side of the turbine main body are connected by the supportmember that can absorb thermal expansion, and the legs for mounting theturbine main body are connected to the outer shell member. Accordingly,because the outer shell member and the support member have highrigidities, the bending stress due to the weight of the turbine mainbody can be sufficiently supported, and the thermal expansion of theturbine main body can be absorbed by the support member. Consequently,the bending stress and the thermal stress applied to the turbine mainbody are reduced, thereby enhancing the durability.

In the support structure of the turbine according to the twelfth aspect,the exhaust chamber through which combustion gas flows is provided asthe turbine main body. The exhaust chamber and the outer shell memberare connected by the support member, and the exhaust duct is connectedto the outer shell member. Accordingly, because the outer shell memberand the support member have high rigidities, the bending stress due tothe weight of the exhaust chamber can be sufficiently supported, and thesupport member can absorb the thermal expansion of the exhaust chamberand the exhaust duct.

In the support structure of the turbine according to the thirteenthaspect, the high-temperature expansion joint is interposed between theouter shell member and the exhaust duct. Accordingly, the thermalexpansion between the exhaust chamber and the exhaust duct can beeffectively absorbed by the high-temperature expansion joint, therebyenhancing the durability.

In the support structure of the turbine according to the fourteenthaspect, the support member is formed in a plurality of strips, and oneend thereof is connected to the end of the exhaust chamber and the otherend is connected to the end of the outer shell member. Being formed intostrips, the support members have high rigidities, thereby suitablysupporting the bending stress due to the weight of the exhaust chamber.

In the support structure of the turbine according to the fifteenthaspect, the gas seal for connecting the exhaust chamber and the outershell member are provided outside the support member. Accordingly, it ispossible to prevent the exhaust gas from leaking from the connectionportion between the exhaust chamber and the exhaust duct.

In the support structure of the turbine according to the sixteenthaspect, the support member is formed in a truncated cone shape, and oneend thereof in the axial direction is connected to the end of theexhaust chamber, and the other end is connected to the end of the outershell member. Being formed into a truncated cone shape, the supportmember has a high rigidity, thereby suitably supporting the bendingstress due to the weight of the exhaust chamber.

The gas turbine according to the seventeenth aspect includes thecompressor, the combustor, and the turbine. The exhaust chamber of theturbine and the outer shell member formed in a ring shape disposed atthe outer peripheral side of the exhaust chamber are connected by thesupport member that can absorb thermal expansion. The outer shell memberand the exhaust duct are connected, and the legs for mounting theexhaust chamber are connected to the outer shell member. Accordingly,because the outer shell member and the support member have highrigidities, the bending stress due to the weight of the turbine mainbody can be sufficiently supported, and the thermal expansion of theturbine main body can be absorbed by the support member. Consequently,the bending stress and the thermal stress applied to the turbine mainbody are reduced, thereby enhancing the durability.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is a sectional view of an essential portion of a turbineillustrating a connection structure of an exhaust chamber in a gasturbine according to a first embodiment of the present invention.

FIG. 2 is a sectional view of a connection portion between an exhaustcasing and the exhaust chamber in the gas turbine of the firstembodiment.

FIG. 3 is a plan view of the connection portion between the exhaustcasing and the exhaust chamber.

FIG. 4 is a sectional view of a connection portion between the exhaustchamber and an exhaust duct in the gas turbine of the first embodiment.

FIG. 5 is a schematic of the gas turbine of the first embodiment.

FIG. 6 is a sectional view of an essential portion of a turbineillustrating a support structure of a turbine in a gas turbine accordingto a second embodiment of the present invention.

FIG. 7 is a sectional view taken along the line A-A in FIG. 1illustrating the support structure of the turbine of the secondembodiment.

FIG. 8 is a sectional view of a connection portion between an exhaustchamber and an exhaust duct in the gas turbine of the second embodiment.

FIG. 9 is a plan view of the connection portion between the exhaustchamber and the exhaust duct.

FIG. 10 is a schematic of the gas turbine of the second embodiment.

FIG. 11 is a sectional view of an essential portion of a turbineillustrating a support structure of a turbine in a gas turbine accordingto a third embodiment of the present invention.

EXPLANATIONS OF LETTERS OR NUMERALS

-   11 compressor-   12 combustor-   13 turbine-   14, 101 exhaust chamber (turbine main body)-   20 turbine casing-   23, 41 exhaust diffuser-   27 exhaust casing (connection member, turbine main body)-   31 exhaust duct (connection member, turbine main body)-   32 exhaust chamber support (support member)-   33, 103 exhaust duct support (support member)-   34, 105 expansion joint (high-temperature expansion joint)-   41 exhaust diffuser-   48 diffuser support-   51, 59, 60, 74 gas seal-   62, 63, 80, 86, 87, 88 insulator-   71, 102 outer shell member-   92 exhaust chamber leg

BEST MODE(S) FOR CARRYING OUT THE INVENTION

Exemplary embodiments of a connection structure of an exhaust chamber, asupport structure of a turbine, and a gas turbine according to thepresent invention are described below in detail with reference to theaccompanying drawings. However, the present invention is not limited bythe embodiments.

First Embodiment

FIG. 1 is a sectional view of an essential portion of a turbineillustrating a connection structure of an exhaust chamber in a gasturbine according to a first embodiment of the present invention. FIG. 2is a sectional view of a connection portion between an exhaust casingand the exhaust chamber in the gas turbine of the first embodiment. FIG.3 is a plan view of the connection portion between the exhaust casingand the exhaust chamber. FIG. 4 is a sectional view of a connectionportion between the exhaust chamber and an exhaust duct in the gasturbine of the first embodiment. FIG. 5 is a schematic of the gasturbine of the first embodiment.

The gas turbine of the present embodiment, as shown in FIG. 5, includesa compressor 11, a combustor 12, a turbine 13, and an exhaust chamber14. A generator, which is not shown, is connected to this gas turbine13. This compressor 11 includes an air inlet port 15 for taking in air,a compressor casing 16 in which a plurality of nozzles 17 and rotorblades 18 are alternately arranged, and a bleed air manifold 19 providedat the outside. The combustor 12 supplies fuel to compressed aircompressed by the compressor 11, and the compressed air and fuel areburned by being ignited by a burner. The turbine 13 includes a turbinecasing 20 in which a plurality of nozzles 21 and rotor blades 22 arealternately arranged. The exhaust chamber 14 is disposed downstream ofthe turbine casing 20 interposing an exhaust casing 27 therebetween. Theexhaust chamber 14 includes an exhaust diffuser 23 continued to theturbine 13. A rotor (turbine shaft) 24 is placed so as to penetratethrough the center portions of the compressor 11, the combustor 12, theturbine 13, and the exhaust chamber 14. The end of the rotor 24 at theside of the compressor 11 is rotatably supported by a bearing portion25, and the other end of the rotor 24 at the side of the exhaust chamber14 is rotatably supported by a bearing portion 26. The rotor 24 isformed of a plurality of disks on which rotor blades 18 and 22 areplaced, and a driving shaft of the generator, which is not shown, isconnected to the end at the side of the exhaust chamber 14.

Accordingly, the air taken in from the air inlet port 15 of thecompressor 11 is turned into high-temperature and high-pressurecompressed air, by passing through the nozzles 21 and the rotor blades22, and being compressed. In the combustor 12, a predetermined fuel issupplied to the compressed air to be combusted. The high-temperature andhigh-pressure combustion gas that is working fluid produced in thecombustor 12 passes through the nozzles 21 and the rotor blades 22 ofthe turbine 13, thereby rotatably driving the rotor 24 and driving thegenerator connected to the rotor 24. The exhaust gas is converted intostatic pressure by the exhaust diffuser 23 in the exhaust chamber 14 andthen released to the atmosphere.

In the turbine 13 described above, as shown in FIG. 1, the exhaustcasing 27 is placed downstream of the turbine casing 20 in which thenozzles 21 and the rotor blades 22 are alternately arranged. The exhaustcasing 27 is formed in a cylindrical shape. The exhaust chamber 14 isdisposed downstream of the exhaust casing 27 in the flowing direction ofthe exhaust gas. The exhaust chamber 14 is formed in a cylindricalshape. An exhaust duct 31 is disposed downstream of the exhaust chamber14 in the flowing direction of the exhaust gas. The exhaust duct 31 isformed in a cylindrical shape. The exhaust casing 27 and the exhaustchamber 14 are connected by an exhaust chamber support (support member)32 that can absorb thermal expansion. The exhaust chamber 14 and theexhaust duct 31 are connected by an exhaust duct support (supportmember) 33 that can absorb thermal expansion and an expansion joint(high-temperature expansion joint) 34 that can absorb thermal expansion.

An exhaust diffuser 41 formed in a cylindrical shape is disposed insidethe exhaust casing 27. The exhaust diffuser 41 includes an outerdiffuser 42 and an inner diffuser 43 formed in cylindrical shapesconnected by a strut shield 44. The strut shield 44 has a hollowstructure such as a cylindrical shape or an elliptic cylindrical shape,and is provided in plurality at equal intervals in the circumferentialdirection of the exhaust diffuser 41. At the inner periphery of theinner diffuser 43, the rotor 24 is rotatably supported through a bearing45, and an oil pipe 46 for supplying lubricating oil to the bearing 45is disposed. A strut 47 is disposed in each of the strut shields 44.Cool air is supplied from outside to a space inside the exhaust diffuser41, and a space between the exhaust casing 27 and the exhaust diffuser41, through the space inside the strut shield 44. A diffuser support 48,which will be described later, is also cooled by this cool air. One ofthe ends of the strut 47 is fixed to the exhaust casing 27, and theother end is fixed to a bearing box.

The exhaust casing 27 and the exhaust diffuser 41 are connected by thediffuser support 48. The diffuser support 48 extends in the axialdirection of the turbine 13 in the form of a strip, and a pluralitythereof is arranged side by side at predetermined intervals in thecircumferential direction. If thermal expansion occurs due to thetemperature difference between the exhaust casing 27 and the exhaustdiffuser 41, each of the diffuser supports 48 absorbs the thermalexpansion by deforming its shape. In particular, the thermal expansiontends to occur during a transition period such as at the start of theturbine 13. One of the ends of the diffuser support 48 is fastened tothe exhaust casing 27 by a bolt 49, and the other end is fastened to theouter diffuser 42 by a bolt 50. The exhaust casing 27 is provided so asto cover the diffuser supports 48 from outside. A gas seal 51 isprovided between the outer diffuser 42 and the exhaust casing 27,thereby shielding the exhaust casing from the turbine casing.

The exhaust chamber 14 includes an outer casing 52 and an inner cylinder53 formed in cylindrical shapes connected by a follow strut 54. Thefollow strut 54 has a hollow structure such as a cylindrical shape or anelliptic cylindrical shape, and is provided in plurality at equalintervals in the circumferential direction of the exhaust chamber 14.Each of the follow struts 54 is opened at the side of the outer casing52 of the exhaust chamber 14, and the inside of the follow strut 54communicates with the atmosphere.

The exhaust casing 27 and the exhaust chamber 14 are connected by theexhaust chamber support 32. In the exhaust diffuser 41 and the exhaustchamber 14, the ends of the outer diffuser 42 and the outer casing 52,and the inner diffuser 43 and the inner cylinder 53 are closely facingeach other. The diameters of the outer diffuser 42 and the outer casing52 are enlarged toward the downstream in the flowing direction of theexhaust gas. However, the diameters of the inner diffuser 43 and theinner cylinder 53 are the same toward the downstream in the flowingdirection of the exhaust gas. The end of the exhaust casing 27 placed atthe outer peripheral side than the outer diffuser 42 of the exhaustdiffuser 41, and the end of the outer casing 52 of the exhaust chamber14 are connected by the exhaust chamber support 32.

The exhaust chamber support 32 extends in the axial direction of theturbine 13 in the form of a strip, and a plurality thereof is arrangedside by side at predetermined intervals in the circumferentialdirection. If thermal expansion occurs due to the temperature differencebetween the exhaust casing 27 and the exhaust chamber 14, each of theexhaust chamber supports 32 absorbs the thermal expansion by deformingits shape. The thermal expansion tends to occur during a transitionperiod such as at the start of the turbine 13 and during heavy loadoperation.

As shown in FIGS. 2 and 3, a connection ring 55 is fixed to the end ofthe exhaust casing 27 by a bolt 56. A connection flange 32 a that is oneof the ends of the exhaust chamber support 32 is fastened to thisconnection ring 55 by bolts 57, and a connection flange 32 b that is theother end of the exhaust chamber support 32 is fastened to a mountingflange 52 a of the outer casing 52 in the exhaust chamber 14 by bolts58. A gas seal 59 is provided between the downstream end of the exhaustcasing 27 and the downstream end of the outer diffuser 42. A gas seal 60is provided between the connection ring 55 and the upstream end of theouter casing 52, at the inside of the exhaust chamber support 32. Arubber seal 61 is provided between the ends of the inner diffusers 43and 53.

The gas seal 59 serves to confine the cool air supplied through theinside of the strut shield 44 to between the outer diffuser 41 and theexhaust casing 27.

An insulator 62 is mounted on the outer peripheral surface of theexhaust casing 27. Similarly, an insulator 63 is mounted on the outerperipheral surface of the exhaust chamber 14. The exhaust chambersupports 32 are provided outside the outer casing 52 of the exhaustchamber 14, and the exhaust chamber supports 32 are disposed outside theinsulator 63. The exhaust chamber support 32 can be cooled by theoutside air. The insulator 63 is disposed so as to avoid the opening ofthe follow strut 54 so as not to block the air intake.

The exhaust duct 31 shown in FIGS. 1 and 4 is formed in a cylindricalshape, and connected to the exhaust chamber 14 by the exhaust ductsupport 33 and the expansion joint 34. An outer shell member 71 formedin a ring shape is disposed at the outer peripheral side of the end ofthe exhaust chamber 14. The end of the exhaust chamber 14 and the innerperiphery of the outer shell member 71 are connected by the exhaust ductsupport 33. The exhaust duct support 33 extends in the axial directionof the turbine 13 in the form of a strip, and a plurality thereof isarranged side by side at predetermined intervals in the circumferentialdirection. If thermal expansion occurs due to the temperature differencebetween the exhaust chamber 14 and the exhaust duct 31, each of theexhaust duct supports 33 absorbs the thermal expansion by deforming itsshape. In particular, the thermal expansion tends to occur during atransition period such as at the start of the turbine 13 and duringheavy load operation. The cross-section of the outer shell member 71 isformed in a U-shape opened to the outside, and the outer shell member 71includes a mounting flange 71 a at the inner peripheral surface and aconnection flange 71 b at the outer periphery.

A connection flange 33 a that is one of the ends of the exhaust ductsupport 33 is fastened to the mounting flange 71 a of the outer shellmember 71 by bolts 72, and a connection flange 33 b that is the otherend of the exhaust duct support 33 is fastened to a connection flange 52b of the outer casing 52 of the exhaust chamber 14 by bolts 73. A gasseal 74 is provided between the mounting flange 71 a of the outer shellmember 71 and the outer casing 52, at the outside of the exhaust ductsupports 33.

In the expansion joint 34, support flanges 77 and 78 are placed uprighton a pair of mounting flanges 75 and 76 formed in a ring shape, and themounting flanges 75 and 76 are bridged across and connected by a lockingseal 79 formed in a ring shape. An insulator 80 is filled into a spaceformed by the support flanges 77 and 78, and the locking seal 79. Theinsulator 80 is covered by a boot 81. The ends of the boot 81 arefastened to the support flanges 77 and 78 by bolts 82 and 83. Themounting flange 75 is fastened to the connection flange 71 b of theouter shell member 71 by a bolt 84, and the mounting flange 76 isfastened to the end of the exhaust duct 31 by a bolt 85. The expansionjoint 34 insulates between the exhaust chamber 14 and the exhaust duct31 during heavy load operation performed by the turbine 13, and ifthermal expansion occurs due to the temperature difference, theexpansion joint 34 absorbs the thermal expansion by deforming its shape.

Insulators 86 and 87 are mounted on the inner peripheral surface of themounting flanges 75 and 76, and an insulator 88 is mounted on the innerperipheral surface of the exhaust duct 31. The expansion joint 34 isdisposed outside the insulators 86, 87, and 88, and cooled by theoutside air.

In this manner, in the connection structure of the exhaust chamber ofthe present embodiment, the exhaust chamber 14 and the exhaust casing 27disposed upstream of the exhaust chamber 14 in the flowing direction ofthe exhaust gas, are connected by the exhaust chamber supports 32 thatcan absorb thermal expansion. The insulator 63 is mounted on the outerperipheral surface of the exhaust chamber 14, and the exhaust chambersupports 32 are disposed outside the insulator 63 in the form of strips.One of the ends of the exhaust chamber support 32 is connected to theend of the exhaust chamber 14, and the other end is connected to the endof the exhaust casing 27.

Accordingly, because the exhaust chamber supports 32 are formed instrips and can be deformed easily, the exhaust chamber supports 32 caneffectively absorb the thermal expansion that occurs between the exhaustchamber 14 and the exhaust casing 27. Because the exhaust chambersupports 32 are disposed outside the insulator 63, the exhaust chambersupports 32 are sufficiently cooled by the outside air. As a result, thethermal stress at a connection portion between the exhaust chamber 14and the exhaust casing 27, in other words, at the exhaust chambersupport 32 is reduced, thereby enhancing the durability.

In this case, the gas seals 59 and 60 for connecting the exhaust chamber14 and the exhaust casing 27 are provided inside the exhaust chambersupports 32. Accordingly, it is possible to prevent the exhaust gas fromleaking from the connection portion between the exhaust chamber 14 andthe exhaust casing 27 to the outside. Because the exhaust chambersupports 32 and the exhaust casing 27 are separated fromhigh-temperature exhaust gas, the thermal expansions thereof can beprevented.

In the connection structure of the exhaust chamber of the presentembodiment, the exhaust diffuser 41 formed in a cylindrical shape isdisposed inside the exhaust casing 27, and the exhaust casing 27 and theexhaust diffuser 41 are connected by the diffuser supports 48 that canabsorb thermal expansion in the form of strips. Accordingly, the thermalexpansion that occurs due to the temperature difference between theexhaust casing 27 and the exhaust diffuser 41 can be effectivelyabsorbed, thereby enhancing the durability.

In the connection structure of the exhaust chamber of the presentembodiment, the exhaust chamber 14 and the exhaust duct 31 disposeddownstream of the exhaust chamber 14 in the flowing direction of theexhaust gas, are connected by the exhaust duct supports 33 that canabsorb thermal expansion. The insulator 63 is mounted on the outerperipheral surface of the exhaust chamber 14, and the exhaust ductsupports 33 are disposed outside the insulator 63 in the form of strips.One of the ends of the exhaust duct support 33 is connected to the endof the exhaust chamber 14, and the other end is connected to the end ofthe exhaust duct 31.

Accordingly, because the exhaust duct supports 33 are formed in stripsand can be deformed easily, the thermal expansion that occurs betweenthe exhaust chamber 14 and the exhaust duct 31 can be effectivelyabsorbed. Because the expansion joint 34 is disposed outside the exhaustduct supports 33, the expansion joint 34 is sufficiently cooled by theoutside air. The expansion joint 34 is protected from heat by theexhaust duct supports 33 provided inside.

In this case, because the gas seal 74 for connecting the exhaust chamber14 and the exhaust duct 31 is provided outside the exhaust duct supports33, it is possible to prevent the exhaust gas from leaking from theconnection portion between the exhaust chamber 14 and the exhaust duct31 to the outside.

In the connection structure of the exhaust chamber according to thepresent embodiment, the outer shell member 71 formed in a ring shape isdisposed at the outer peripheral side of the exhaust chamber 14, and theexhaust duct 31 is disposed adjacent to the outer shell member 71. Theexhaust chamber 14 and the outer shell member 71 are connected by theexhaust duct supports 33, and the outer shell member 71 and the exhaustduct 31 are connected by the expansion joint 34. Accordingly, theexpansion joint 34 can be sufficiently cooled, thereby enhancing thedurability.

In this case, because the insulator 88 is mounted on the innerperipheral surface of the exhaust duct 31, the temperature of the innersurface is maintained. Accordingly, the temperature of the exhaust duct31 can be reduced, and the temperature of the expansion joint 34 can beprevented from being increased, thereby enhancing the durability.

The gas turbine of the present embodiment includes the compressor 11,the combustor 12, and the turbine 13. The exhaust casing 27 of theturbine 13 and the exhaust chamber 14 are connected by the exhaustchamber supports 32, and the exhaust chamber 14 and the exhaust duct 31are connected by the exhaust duct supports 33. The insulator 63 ismounted on the outer peripheral surface of the exhaust chamber 14, andthe exhaust chamber supports 32 and the exhaust duct supports 33 aredisposed outside the insulator 63 in the form of strips.

Accordingly, because the exhaust chamber supports 32 and the exhaustduct supports 33 are formed in strips and can be deformed easily, thethermal expansions that occur between the exhaust casing 27, the exhaustchamber 14, and the exhaust duct 31 can be effectively absorbed. Becausethe exhaust chamber supports 32 and the exhaust duct supports 33 aredisposed outside the insulator 63, the supports 32 and 33 aresufficiently cooled by the outside air. As a result, the thermalstresses at the connection portions of the exhaust casing 27, theexhaust chamber 14, and the exhaust duct 31, in other words, at thesupports 32 and 33 are reduced, thereby enhancing the durability.Consequently, the power and efficiency of the turbine can be enhanced.

Second Embodiment

FIG. 6 is a sectional view of an essential portion of a turbineillustrating a support structure of a turbine in a gas turbine accordingto a second embodiment of the present invention. FIG. 7 is a sectionalview taken along the line A-A in FIG. 6 illustrating the supportstructure of the turbine of the second embodiment. FIG. 8 is a sectionalview of a connection portion between an exhaust chamber and an exhaustduct in the gas turbine of the second embodiment. FIG. 9 is a plan viewof the connection portion between the exhaust chamber and the exhaustduct. FIG. 10 is a schematic of the gas turbine of the second embodiment

The gas turbine of the present embodiment, as shown in FIG. 10, includesthe compressor 11, the combustor 12, the turbine 13, and the exhaustchamber 14. A generator, which is not shown, is connected to this gasturbine 13. This compressor 11 includes the air inlet port 15 for takingin air, the compressor casing 16 in which the nozzles 17 and the rotorblades 18 are alternately arranged, and the bleed air manifold 19provided at the outside. The combustor 12 supplies fuel to compressedair compressed by the compressor 11, and the compressed air and fuel areburned by being ignited by a burner. The turbine 13 includes the turbinecasing 20 in which the nozzles 21 and the rotor blades 22 arealternately arranged. The exhaust chamber 14 is disposed downstream ofthe turbine casing 20 interposing the exhaust casing 27 therebetween.The exhaust chamber 14 includes the exhaust diffuser 23 continued to theturbine 13. The rotor (turbine shaft) 24 is placed so as to penetratethrough the center portions of the compressor 11, the combustor 12, theturbine 13, and the exhaust chamber 14. The end of the rotor 24 at theside of the compressor 11 is rotatably supported by the bearing portion25, and the end of the rotor 24 at the side of the exhaust chamber 14 isrotatably supported by the bearing portion 26. The rotor 24 is formed ofthe disks on which the rotor blades 18 and 22 are placed, and a drivingshaft of the generator, which is not shown, is connected to the end atthe side of the exhaust chamber 14.

Accordingly, the air taken in from the air inlet port 15 of thecompressor 11 is turned into high-temperature and high-pressurecompressed air, by passing through the nozzles 17 and the rotor blades18, and being compressed. In the combustor 12, a predetermined fuel issupplied to the compressed air to be combusted. The high-temperature andhigh-pressure combustion gas that is working fluid produced in thecombustor 12 passes through the nozzles 21 and the rotor blades 22 ofthe turbine 13, thereby rotatably driving the rotor 24 and driving thegenerator connected to the rotor 24. The exhaust gas is converted intostatic pressure by the exhaust diffuser 23 in the exhaust chamber 14 andthen released to the atmosphere.

In the turbine 13 described above, as shown in FIGS. 6 and 7, theexhaust casing 27 is placed downstream of the turbine casing 20 in whichthe nozzles 21 and the rotor blades 22 (see FIG. 10) are alternatelyarranged. The exhaust casing 27 is formed in a cylindrical shape. Theexhaust chamber 14 is disposed downstream of the exhaust casing 27 inthe flowing direction of the exhaust gas. The exhaust chamber 14 isformed in a cylindrical shape. The exhaust duct 31 is disposeddownstream of the exhaust chamber 14 in the flowing direction of theexhaust gas. The exhaust duct 31 is formed in a cylindrical shape. Theexhaust casing 27 and the exhaust chamber 14 are connected by theexhaust chamber support 32 that can absorb thermal expansion. Theexhaust chamber 14 and the exhaust duct 31 are connected by the exhaustduct support (support member) 33 that can absorb thermal expansion andthe expansion joint (high-temperature expansion joint) 34 that canabsorb thermal expansion.

In this case, in the present embodiment, the outer shell member 71formed in a ring shape is disposed downstream of the end of the exhaustchamber 14 as a turbine main body in the flowing direction of theexhaust gas, at the outer peripheral side. The exhaust chamber 14 andthe outer shell member 71 are connected by the exhaust duct support 33,and the outer shell member 71 and the exhaust duct 31 are connected bythe expansion joint 34. Exhaust chamber legs 92 for mounting the exhaustchamber 14 are connected to the outer shell member 71.

The exhaust diffuser 41 formed in a cylindrical shape is disposed insidethe exhaust casing 27. The exhaust diffuser 41 includes the outerdiffuser 42 and the inner diffuser 43 formed in cylindrical shapesconnected by the strut shield 44. The strut shield 44 has a hollow shapesuch as a cylindrical shape or an elliptic cylindrical shape, and isprovided in plurality at equal intervals in the circumferentialdirection of the exhaust diffuser 41. At the inner periphery of theinner diffuser 43, the rotor 24 is rotatably supported through thebearing 45, and the oil pipe 46 for supplying lubricating oil to thebearing 45 is disposed. The strut 47 is disposed in each of the strutshields 44. Cool air is supplied to a space inside the exhaust diffuser41 and a space between the exhaust casing 27 and the exhaust diffuser 41from outside, through the space inside the strut shield 44. The diffusersupport 48, which will be described later, is also cooled by this coolair. One of the ends of the strut 44 is fixed to the exhaust casing 27,and the other end is fixed to a bearing box.

The exhaust casing 27 and the exhaust diffuser 41 are connected by thediffuser support 48. The diffuser support 48 extends in the axialdirection of the turbine 13 in the form of a strip, and a pluralitythereof is arranged side by side at predetermined intervals in thecircumferential direction. If thermal expansion occurs due to thetemperature difference between the exhaust casing 27 and the exhaustdiffuser 41, each of the diffuser supports 48 absorbs the thermalexpansion by deforming its shape. In particular, the thermal expansiontends to occur during a transition period such as at the start of theturbine 13. One of the ends of the diffuser support 48 is fastened tothe exhaust casing 27 by the bolt 49, and the other end is fastened tothe outer diffuser 42 by the bolt 50. The exhaust casing 27 is providedso as to cover the diffuser supports 48 from outside. The gas seal 51 isprovided between the outer diffuser 42 and the exhaust casing 27,thereby shielding the exhaust casing 27 from the turbine casing 20.

The exhaust chamber 14 includes the outer casing 52 and the innercylinder 53 formed in cylindrical shapes connected by the follow strut54. The follow strut 54 has a hollow shape such as a cylindrical shapeor an elliptic cylindrical shape, and is provided in plurality at equalintervals in the circumferential direction of the exhaust chamber 14.Each of the follow struts 54 is opened at the side of the outer casing52 of the exhaust chamber 14, and the inside of the follow strut 54communicates with the atmosphere.

The exhaust casing 27 and the exhaust chamber 14 are connected by theexhaust chamber support 32. In the exhaust diffuser 41 and the exhaustchamber 14, the ends of the outer diffuser 42 and the outer casing 52,and the inner diffuser 43 and the inner cylinder 53 are closely facingeach other. The diameters of the outer diffuser 42 and the outer casing52 are enlarged toward the downstream in the flowing direction of theexhaust gas. However, the diameters of the inner diffuser 43 and theinner cylinder 53 are the same toward the downstream in the flowingdirection of the exhaust gas. The end of the exhaust casing 27 placed atthe outer peripheral side than the outer diffuser 42 of the exhaustdiffuser 41 and the end of the outer casing 52 of the exhaust chamber 14are connected by the exhaust chamber support 32.

The exhaust chamber support 32 extends in the axial direction of theturbine 13 in the form of a strip, and a plurality thereof is arrangedside by side at predetermined intervals in the circumferentialdirection. If thermal expansion occurs due to the temperature differencebetween the exhaust casing 27 and the exhaust chamber 14, each of theexhaust chamber supports 32 absorbs the thermal expansion by deformingits shape. The thermal expansion tends to occur during a transitionperiod such as at the start of the turbine 13 and during heavy loadoperation.

The connection ring 55 is fixed to the end of the exhaust casing 27 bythe bolt 56. The connection flange 32 a that is one of the ends of theexhaust chamber support 32 is fastened to the connection ring 55 by thebolts 57, and the connection flange 32 b that is the other end of theexhaust chamber support 32 is fastened to the mounting flange 52 a ofthe outer casing 52 in the exhaust chamber 14 by the bolts 58. The gasseal 59 is provided between the downstream end of the exhaust casing 27and the downstream end of the outer diffuser 42. The gas seal 60 isplaced inside the exhaust chamber supports 32 between the connectionring 55 and the upstream end of the outer casing 52. The rubber seal 61is provided between the ends of the inner diffuser 43 and the innercylinder 53.

The gas seal 59 serves to confine the cool air supplied through theinside of the strut shield 44 to between the outer diffuser 41 and theexhaust casing 27.

The insulator 62 is mounted on the outer peripheral surface of theexhaust casing 27. Similarly, the insulator 62 is mounted on the outerperipheral surface of the exhaust chamber 14. The exhaust chambersupports 32 are provided outside the outer casing 52 of the exhaustchamber 14, and the exhaust chamber supports 32 are disposed outsidethis insulator 63. The exhaust chamber supports 32 can be cooled by theoutside air. The insulator 63 is disposed so as to avoid the opening ofthe follow strut 54, so as not to block the air intake.

The exhaust duct 31 shown in FIGS. 6 to 10 is formed in a cylindricalshape, and connected to the exhaust chamber 14 by the exhaust ductsupport 33 and the expansion joint 34. The outer shell member 71 formedin a ring shape is disposed at the outer peripheral side of the end ofthe exhaust chamber 14. The end of the exhaust chamber 14 and the innerperiphery of the outer shell member 71 are connected by the exhaust ductsupport 33. The exhaust duct support 33 extends in the axial directionof the turbine 13 in the form of a strip, and a plurality thereof isarranged side by side at predetermined intervals in the circumferentialdirection. If thermal expansion occurs due to the temperature differencebetween the exhaust chamber 14 and the exhaust duct 31, each of theexhaust duct supports 33 absorbs the thermal expansion by deforming itsshape. In particular, the thermal expansion tends to occur during atransition period such as at the start of the turbine 13 and duringheavy load operation. The cross section of the outer shell member 71 isformed in a U-shape opened to the outside. The outer shell member 71includes an outer shell main body 71 a substantially parallel to theouter peripheral surface of the exhaust chamber 14, the connectionflanges 71 b and 71 c that stand upright from both sides of the outershell main body 71 a substantially perpendicular to the outer peripheralsurface of the exhaust chamber 14, and a connection flange 71 dprojected to the outer peripheral surface side of the exhaust chamber 14from the outer shell main body 71 a.

The connection flange 33 a that is one of the ends of the exhaust ductsupport 33 is fastened to the mounting flange 71 d of the outer shellmember 71 by the bolts 72. The connection flange 33 b that is the otherend of the exhaust duct support 33 is fastened to the connection flange52 b of the outer casing 52 of the exhaust chamber 14 by the bolts 73.The gas seal 74 is provided between the mounting flange 71 b of theouter shell member 71 and the outer casing 52, at the outside of theexhaust duct supports 33.

At the expansion joint 34, the support flanges 77 and 78 are placedupright on the pair of mounting flanges 75 and 76 formed in a ringshape, and the mounting flanges 75 and 76 are bridged across andconnected by the locking seal 79 formed in a ring shape. The insulator80 is filled into a space formed by the support flanges 77 and 78, andthe locking seal 79. The insulator 80 is covered by the boot 81. Theends of the boot 81 are fastened to the support flanges 77 and 78 by thebolts 82 and 83. The mounting flange 75 is fastened to the connectionflange 71 b of the outer shell member 71 by the bolt 84, and themounting flange 76 is fastened to the end of the exhaust duct 31 by thebolt 85. The expansion joint 34 insulates between the exhaust chamber 14and the exhaust duct 31 during heavy load operation performed by theturbine 13, and if thermal expansion occurs due to the temperaturedifference, the expansion joint 34 absorbs the thermal expansion bydeforming its shape.

The insulators 86 and 87 are mounted on the inner peripheral surfaces ofthe mounting flanges 75 and 76, and the insulator 88 is mounted on theinner peripheral surface of the exhaust duct 31. The expansion joint 34is disposed outside the insulators 86, 87, and 88, and cooled by theoutside air.

As shown in FIGS. 6 and 7, in the outer shell member 71 connected to theexhaust chamber 14 interposing the exhaust duct supports 33 in the formof strips therebetween, mounting brackets 91 are fixed to both sides ofthe outer shell main body 71 a, and exhaust chamber legs 92 areconnected to the mounting brackets 91. Accordingly, the exhaust chamber14 is mounted on the floor of a turbine building, which is not shown, bythe two exhaust chamber legs 92. In other words, the exhaust chamber 14is supported by the outer shell member 71 interposing the exhaust ductsupports 33 arranged side by side in the circumferential directiontherebetween, and the outer shell member 71 is mounted on the floor bythe exhaust chamber legs 92.

In this case, the exhaust duct supports 33 are formed in strips having apredetermined width, and mounted in the longitudinal direction (flowingdirection of exhaust gas) of the exhaust chamber 14. Because the exhaustduct supports 33 are arranged side by side in the circumferentialdirection of the exhaust chamber 14, each of the exhaust duct supports33 has a high rigidity in the vertical (circumferential) direction.Because the cross-section of the outer shell member 71 is irregular inwhich the connection flange 71 d is added to the U-shaped cross sectionof the outer shell main body 71 a and the connection flanges 71 b and 71c, the outer shell member 71 has a high rigidity in the vertical(circumferential) direction. Accordingly, the exhaust duct supports 33and the outer shell member 71 have high rigidities, thereby sufficientlysupporting the weight of the exhaust chamber 14. Due to the deformationof the exhaust duct supports 33, the thermal expansion of the exhaustchamber 14 can be sufficiently absorbed.

As shown in FIG. 6, the exhaust duct 31 is mounted on the floor of thebuilding by a plurality of exhaust duct legs 93 and 94. The exhaustcasing 27 is mounted on the floor of the building by exhaust casinglegs, which are not shown.

In this manner, in the support structure of the turbine of the presentembodiment, the outer shell member 71 formed in a ring shape is disposedat the outer peripheral side of the exhaust chamber 14, as the turbinemain body formed in a cylindrical shape. The exhaust chamber 14 and theouter shell member 71 are connected by the exhaust duct supports 33 thatcan absorb thermal expansion, and the exhaust chamber legs 92 formounting the exhaust chamber 14 in the building are connected to theouter shell member 71.

Accordingly, because the outer shell member 71 and the exhaust ductsupports 33 have high rigidities, the bending stress due to the weightof the exhaust chamber 14 can be sufficiently supported, and the thermalexpansion of the exhaust chamber 14 can be absorbed by the exhaust ductsupports 33. Consequently, the bending stress and the thermal stressapplied to the exhaust chamber 14 are reduced, thereby enhancing thedurability.

In the support structure of the turbine of the present embodiment, theexpansion joint 34 is interposed between the outer shell member 71 andthe exhaust duct 31. Accordingly, the thermal expansion between theexhaust chamber 14 and the exhaust duct 31 can be effectively absorbedby the expansion joint 34, thereby enhancing the durability.

In the support structure of the turbine of the present embodiment, theexhaust duct supports 33 are formed in strips, and one of the ends ofthe exhaust duct support 33 is connected to the end of the exhaustchamber 14, and the other end is connected to the end of the outer shellmember 71. Because the exhaust duct supports 33 are formed in strips andhave high rigidities, the exhaust duct supports 33 can suitably supportthe bending stress due to the weight of the exhaust chamber 14.

In the support structure of the turbine of the present embodiment, thegas seal 74 for connecting the exhaust chamber 14 and the outer shellmember 71 is provided outside the exhaust duct supports 33. Accordingly,it is possible to prevent the exhaust gas from leaking from theconnection portion between the exhaust chamber 14 and the exhaust duct31.

The gas turbine of the present embodiment includes the compressor 11,the combustor 12, and the turbine 13. The exhaust chamber 14 of theturbine 13 and the outer shell member 71 formed in a ring shape disposedat the outer peripheral side of the exhaust chamber 14 are connected bythe exhaust duct supports 33 that can absorb thermal expansion. Theouter shell member 71 and the exhaust duct 31 are connected interposingthe expansion joint 34 therebetween, and the exhaust chamber legs 92 formounting the exhaust chamber 14 are connected to the outer shell member71.

Accordingly, because the outer shell member 71 and the exhaust ductsupports 33 have high rigidities, the bending stress due to the weightof the exhaust chamber 14 can be sufficiently supported, and the thermalexpansion of the exhaust chamber 14 can be absorbed by the exhaust ductsupports 33. Consequently, the bending stress and the thermal stressapplied to the exhaust chamber 14 are reduced, thereby enhancing thedurability of the entire gas turbine.

Third Embodiment

FIG. 11 is a sectional view of an essential portion of a turbineillustrating a support structure of a turbine in a gas turbine accordingto a third embodiment of the present invention.

In the support structure of the turbine in the gas turbine of thepresent embodiment, as shown in FIG. 11, an exhaust chamber 101 as aturbine main body is formed in a cylindrical shape. An outer shellmember 102 formed in a ring shape is disposed downstream of the end ofthe exhaust chamber 101 in the flowing direction of the exhaust gas, atthe outer peripheral side, and the exhaust chamber 101 and the outershell member 102 are connected by an exhaust duct support (supportmember) 103. An exhaust duct 104 is disposed downstream of the exhaustchamber 101 in the flowing direction of the exhaust gas. The exhaustduct 104 is formed in a cylindrical shape, and the outer shell member102 and the exhaust duct 104 are connected by an expansion joint(high-temperature expansion joint) 105. Exhaust chamber legs, which arenot shown, for mounting the exhaust chamber 101 are connected to theouter shell member 102.

In other words, the outer shell member 102 formed in a ring shape isdisposed at the outer peripheral side of the end of the exhaust chamber101. The end of the exhaust chamber 101 and the inner periphery of theouter shell member 102 are connected by the exhaust duct support 103.The exhaust duct support 103 is formed in a truncated cone shape. Ifthermal expansion occurs due to the temperature difference between theexhaust chamber 101 and the exhaust duct 104, the exhaust duct support103 absorbs the thermal expansion by deforming its shape. In particular,the thermal expansion tends to occur during a transition period such asat the start of the turbine and during heavy load operation. Thecross-section of the outer shell member 102 is formed in a U-shapeopened to the outside. The outer shell member 102 includes an outershell main body 102 a substantially parallel to the outer peripheralsurface of the exhaust chamber 101, connection flanges 102 b and 102 cthat stand upright from both sides of the outer shell main body 102 asubstantially perpendicular to the outer peripheral surface of theexhaust chamber 101, and a connection flange 102 d projected to theouter peripheral surface side of the exhaust chamber 101 from the outershell main body 102 a. One of the ends of the exhaust duct support 103is fastened to the mounting flange 102 d of the outer shell member 102by a bolt 106, and the other end is fixed to the exhaust chamber 101.

In the expansion joint 105, support flanges 109 and 110 are placedupright on a pair of mounting flanges 107 and 108 formed in a ringshape. An insulator 111 is filled into a space formed by the supportflanges 109 and 110, and covered by a bellows 112. A cover 113 isfastened by bolts 114 and 115. The mounting flange 107 is fastened tothe connection flange 102 b of the outer shell member 102 by a bolt 116,and the mounting flange 108 is fastened to the end of the exhaust duct104 by a bolt 117. This expansion joint 105 insulates between theexhaust chamber 101 and the exhaust duct 104 during heavy load operationperformed by the turbine, and if thermal expansion occurs due to thetemperature difference, the expansion joint 105 absorbs the thermalexpansion by deforming its shape.

Although not shown, the exhaust chamber legs are connected to both sidesof the outer shell member 102 interposing mounting bracketstherebetween. Accordingly, the exhaust chamber 101 is mounted on thefloor of the turbine building by two exhaust chamber legs. In otherwords, the exhaust chamber 101 is supported by the outer shell member102 interposing the exhaust duct support 103 therebetween, and the outershell member 102 is mounted on the floor by the exhaust chamber legs.

In this case, because the exhaust duct support 103 is formed in atruncated cone shape, and mounted in the longitudinal direction (flowingdirection of exhaust gas) of the exhaust chamber 101, the exhaust ductsupport 103 has a high rigidity in the vertical (circumferential)direction. Because the cross-section of the outer shell member 102 isirregular in which the connection flange 102 d is added to the U-shapedcross section of the outer shell main body 102 a and the connectionflanges 102 b and 102 c, the outer shell member 102 has a high rigidityin the vertical (circumferential) direction. Accordingly, the exhaustduct support 103 and the outer shell member 102 have high rigidities,thereby sufficiently supporting the weight of the exhaust chamber 101.Due to the deformation of the exhaust duct support 103, the thermalexpansion of the exhaust chamber 101 can also be sufficiently absorbed.

In this manner, in the support structure of the turbine of the presentembodiment, the outer shell member 102 formed in a ring shape isdisposed at the outer peripheral side of the exhaust chamber 101 as aturbine main body formed in a cylindrical shape. The exhaust chamber 101and the outer shell member 102 are connected by the exhaust duct support103 that can absorb thermal expansion, and the exhaust chamber legs formounting the exhaust chamber 101 in the building are connected to theouter shell member 102.

Accordingly, because the outer shell member 102 and the exhaust ductsupport 103 have high rigidities, the bending stress due to the weightof the exhaust chamber 101 can be sufficiently supported, and thethermal expansion of the exhaust chamber 101 can be absorbed by theexhaust duct support 103. Consequently, the bending stress and thethermal stress applied to the exhaust chamber 101 are reduced, therebyenhancing the durability.

In the support structure of the turbine of the present embodiment, theexhaust duct support 103 is formed in a truncated cone shape. One of theends of the exhaust duct support 103 in the axial direction is connectedto the end of the exhaust chamber 101, and the other end is connected tothe end of the outer shell member 102. Being formed into a truncatedcone shape, the exhaust duct support 103 has a high rigidity.Accordingly, the exhaust duct support 103 can suitably support thebending stress due to the weight of the exhaust chamber 101.

In the embodiments described above, the turbine main body of the presentinvention is the exhaust chamber 14. The exhaust chamber 14 and theouter shell member 71 are connected by the exhaust duct supports 33, andthe exhaust chamber legs 92 are connected to the outer shell member 71.However, the present embodiment is not limited to this structure. Inother words, the turbine main body of the present invention may be theexhaust casing 27, and an outer shell member may be provided outsidethis exhaust chamber 14 interposing a support member therebetween, andexhaust casing legs may be connected to this outer shell member.Alternatively, the turbine main body of the present invention may be theexhaust duct 31, and an outer shell member may be provided outside thisexhaust duct 31 interposing a support member therebetween, and theexhaust duct legs may be connected to the outer shell member.

INDUSTRIAL APPLICABILITY

In the connection structure of the exhaust chamber and the gas turbineaccording to the present invention, the insulator is mounted on theouter peripheral surface of the exhaust chamber, and the support membersare disposed outside the insulator in the form of strips. Because thethermal stress at the connection portion of the exhaust chamber isreduced, the durability is enhanced. As a result, the connectionstructure of the exhaust chamber and the gas turbine can be applied toany type of gas turbine.

In the support structure of the turbine and the gas turbine according tothe present invention, the legs are connected to the outer shell memberof the turbine main body interposing the support member that can absorbthermal expansion therebetween. Because the bending stress and thethermal stress applied to the turbine main body are reduced, thedurability is enhanced. As a result, the support structure of theturbine and the gas turbine can be applied to any type of gas turbine.

The invention claimed is:
 1. A support structure of a turbinecomprising: a turbine main body formed in a cylindrical shape, formingan exhaust system, and including an exhaust chamber and an exhaust duct;an outer shell member formed in a ring shape and disposed at an outerperipheral side of the exhaust chamber; and an exhaust chamber leg formounting the turbine main body, wherein the exhaust chamber leg connectsbetween the outer shell member and a floor of a turbine building,wherein the exhaust chamber is disposed upstream of the exhaust duct,the exhaust chamber and the outer shell member are connected by asupport member that is configured to absorb thermal expansion, and theouter shell member and the exhaust duct are connected by ahigh-temperature expansion joint that is configured to absorb thermalexpansion.
 2. The support structure of the turbine according to claim 1,wherein the support member is in a form of a plurality of strips, eachhaving one end connected to a downstream side of the exhaust chamber ina flow direction of an exhaust gas, and another end connected to aninner periphery of the outer shell member.
 3. The support structure ofthe turbine according to claim 1, further comprising: a gas seal thatconnects the exhaust chamber to the outer shell member, and is disposedoutside a connection portion between the support member and the exhaustchamber, and outside a connection portion between the support member andthe outer shell member.
 4. The support structure of the turbineaccording to claim 1, wherein the support member is formed in atruncated cone shape, one end of the support member in an axialdirection is connected to a downstream side of the exhaust chamber in aflow direction of an exhaust gas, and another end of the support memberis connected to an inner periphery of the outer shell member.
 5. Thesupport of the turbine according to claim 1, wherein the outer shellmember is disposed downstream of an end of the exhaust chamber in a flowdirection of an exhaust gas.